FIELD: transport.
SUBSTANCE: invention relates to space engineering and may be used in spacecraft descent in atmosphere of planets. In spacecraft descent measured are temperature (T), speed (first derivative T') and acceleration (second derivative T") of variation of T of spacecraft heating in critical region. In case T'>0 and T"<0 angle of attack is increased to satisfy T'=0 to set angles of bank and attack to allow spacecraft descent conditions for isothermal section (T'=T'=0). Then at T'<0 zero angle of attack is set.
EFFECT: decreased maximum spacecraft heating temperature in critical region.
1 dwg
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